EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 377 AIRFOIL (e377-il) Reynolds number: 500,000 Max Cl/Cd: 133.91 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e377-il-500000.txt Download as CSV file: xf-e377-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 377 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.1385 0.09412 0.09173 -0.0317 0.8418 0.0088
-7.250 -0.1342 0.09296 0.09037 -0.0315 0.7965 0.0089
-7.000 -0.1238 0.09131 0.08860 -0.0333 0.7722 0.0089
-6.750 -0.1115 0.08922 0.08641 -0.0352 0.7526 0.0089
-6.500 -0.0773 0.07195 0.06909 -0.0295 0.6944 0.0091
-6.250 -0.0673 0.06811 0.06522 -0.0300 0.6848 0.0092
-6.000 -0.0715 0.08030 0.07729 -0.0400 0.7095 0.0091
-5.750 -0.0584 0.07724 0.07418 -0.0410 0.6980 0.0093
-5.500 -0.0425 0.07471 0.07160 -0.0428 0.6861 0.0095
-5.250 -0.0246 0.07227 0.06911 -0.0452 0.6762 0.0097
-5.000 -0.0052 0.06982 0.06660 -0.0478 0.6675 0.0099
-4.750 0.0160 0.06733 0.06408 -0.0508 0.6583 0.0103
-4.500 0.0386 0.06480 0.06148 -0.0539 0.6510 0.0106
-4.250 0.0629 0.06222 0.05885 -0.0573 0.6429 0.0112
-4.000 0.0895 0.05962 0.05620 -0.0610 0.6362 0.0119
-3.750 0.1280 0.05745 0.05395 -0.0673 0.6284 0.0128
-3.500 0.1650 0.05504 0.05145 -0.0732 0.6218 0.0130
-3.250 0.1985 0.05136 0.04771 -0.0783 0.6156 0.0132
-3.000 0.2139 0.04836 0.04466 -0.0784 0.6099 0.0140
-2.750 0.2431 0.04619 0.04246 -0.0814 0.6034 0.0152
-2.500 0.2768 0.04384 0.04000 -0.0853 0.5975 0.0161
-2.250 0.3133 0.04148 0.03757 -0.0896 0.5919 0.0175
-2.000 0.3637 0.03983 0.03578 -0.0960 0.5861 0.0189
-1.750 0.4027 0.03767 0.03348 -0.1000 0.5810 0.0190
-1.500 0.4312 0.03387 0.02966 -0.1028 0.5756 0.0202
-1.250 0.4614 0.03224 0.02794 -0.1047 0.5704 0.0219
-1.000 0.5037 0.03093 0.02648 -0.1083 0.5656 0.0267
-0.750 0.5448 0.02959 0.02502 -0.1114 0.5602 0.0273
-0.500 0.5821 0.02624 0.02151 -0.1149 0.5556 0.0283
-0.250 0.6093 0.02487 0.02009 -0.1157 0.5508 0.0296
0.000 0.6407 0.02361 0.01876 -0.1170 0.5458 0.0317
1.000 0.7937 0.01332 0.00725 -0.1243 0.5286 0.0276
1.250 0.8248 0.01133 0.00466 -0.1248 0.5246 0.0266
1.500 0.8533 0.01062 0.00375 -0.1247 0.5199 0.0270
1.750 0.8812 0.01008 0.00308 -0.1244 0.5152 0.0302
2.000 0.9084 0.01002 0.00295 -0.1241 0.5110 0.0373
2.250 0.9359 0.01006 0.00302 -0.1239 0.5064 0.0622
2.500 0.9631 0.01009 0.00307 -0.1236 0.5015 0.0720
2.750 0.9900 0.01016 0.00308 -0.1234 0.4972 0.0799
3.000 1.0171 0.01027 0.00321 -0.1231 0.4926 0.0889
3.250 1.0442 0.01020 0.00317 -0.1229 0.4877 0.0956
3.500 1.0710 0.01027 0.00319 -0.1226 0.4832 0.1035
3.750 1.0980 0.01027 0.00325 -0.1224 0.4781 0.1156
4.000 1.1249 0.01029 0.00333 -0.1221 0.4725 0.1297
4.250 1.1515 0.01039 0.00343 -0.1218 0.4672 0.1459
4.500 1.1784 0.01040 0.00353 -0.1216 0.4611 0.1619
4.750 1.2050 0.01049 0.00363 -0.1213 0.4554 0.1793
5.000 1.2316 0.01056 0.00378 -0.1211 0.4495 0.2006
5.250 1.2582 0.01062 0.00394 -0.1209 0.4432 0.2265
5.500 1.2846 0.01072 0.00411 -0.1206 0.4372 0.2608
5.750 1.3110 0.01075 0.00428 -0.1204 0.4301 0.3201
6.000 1.3397 0.01013 0.00444 -0.1208 0.4230 1.0000
6.250 1.3659 0.01026 0.00462 -0.1205 0.4152 1.0000
6.500 1.3919 0.01043 0.00480 -0.1202 0.4073 1.0000
6.750 1.4176 0.01062 0.00498 -0.1198 0.3982 1.0000
7.000 1.4435 0.01078 0.00519 -0.1195 0.3887 1.0000
7.250 1.4690 0.01098 0.00542 -0.1192 0.3783 1.0000
7.500 1.4943 0.01122 0.00570 -0.1188 0.3669 1.0000
7.750 1.5190 0.01150 0.00596 -0.1184 0.3461 1.0000
8.000 1.5423 0.01197 0.00632 -0.1179 0.3156 1.0000
8.250 1.5644 0.01263 0.00682 -0.1173 0.2776 1.0000
8.500 1.5833 0.01376 0.00763 -0.1165 0.2231 1.0000
8.750 1.6001 0.01514 0.00866 -0.1155 0.1689 1.0000
9.000 1.6171 0.01639 0.00969 -0.1145 0.1280 1.0000
9.250 1.6323 0.01778 0.01082 -0.1132 0.0887 1.0000
9.500 1.6457 0.01928 0.01207 -0.1118 0.0543 1.0000
9.750 1.6512 0.02147 0.01393 -0.1095 0.0154 1.0000
10.000 1.6610 0.02302 0.01547 -0.1074 0.0075 1.0000
10.250 1.6736 0.02412 0.01671 -0.1056 0.0066 1.0000
10.500 1.6833 0.02534 0.01806 -0.1035 0.0062 1.0000
10.750 1.6866 0.02664 0.01951 -0.1005 0.0059 1.0000
11.000 1.6863 0.02823 0.02124 -0.0977 0.0057 1.0000
11.250 1.6841 0.03029 0.02342 -0.0954 0.0055 1.0000
11.500 1.6808 0.03280 0.02606 -0.0938 0.0052 1.0000
11.750 1.6760 0.03580 0.02921 -0.0927 0.0050 1.0000
12.000 1.6654 0.03974 0.03332 -0.0920 0.0047 1.0000
12.250 1.6570 0.04367 0.03740 -0.0916 0.0046 1.0000
12.500 1.6486 0.04773 0.04161 -0.0915 0.0045 1.0000
12.750 1.6435 0.05148 0.04549 -0.0914 0.0045 1.0000
13.000 1.6368 0.05550 0.04964 -0.0915 0.0045 1.0000
13.250 1.6303 0.05960 0.05386 -0.0917 0.0044 1.0000
13.500 1.6230 0.06384 0.05824 -0.0920 0.0044 1.0000
13.750 1.6157 0.06820 0.06273 -0.0924 0.0044 1.0000
14.000 1.6094 0.07256 0.06721 -0.0929 0.0043 1.0000
14.250 1.6037 0.07698 0.07177 -0.0936 0.0043 1.0000
14.500 1.5973 0.08160 0.07652 -0.0943 0.0042 1.0000
14.750 1.5916 0.08623 0.08128 -0.0951 0.0042 1.0000
15.000 1.5861 0.09092 0.08613 -0.0961 0.0041 1.0000
15.250 1.5806 0.09568 0.09104 -0.0971 0.0040 1.0000
15.500 1.5750 0.10056 0.09606 -0.0983 0.0040 1.0000
15.750 1.5691 0.10560 0.10125 -0.0996 0.0039 1.0000
16.000 1.5629 0.11081 0.10661 -0.1011 0.0039 1.0000
16.250 1.5561 0.11622 0.11218 -0.1028 0.0039 1.0000
16.500 1.5489 0.12185 0.11799 -0.1049 0.0039 1.0000
16.750 1.5410 0.12776 0.12407 -0.1072 0.0039 1.0000
17.000 1.5321 0.13402 0.13051 -0.1100 0.0039 1.0000
17.250 1.5224 0.14065 0.13731 -0.1132 0.0039 1.0000
17.500 1.5125 0.14754 0.14438 -0.1168 0.0040 1.0000
17.750 1.5027 0.15457 0.15157 -0.1207 0.0040 1.0000
18.000 1.4913 0.16228 0.15946 -0.1254 0.0040 1.0000
18.250 1.4811 0.16984 0.16718 -0.1301 0.0041 1.0000
18.500 1.4706 0.17779 0.17528 -0.1352 0.0042 1.0000
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Polar data table (+)
Polar graphs
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